FIELD: mechanical engineering. SUBSTANCE: proposed formed-to-shape blade 12 of compressor has high-pressure side 18 and low-pressure side 18 and low-pressure side 20 stretching from shank 22 to top 24 and between leading edge 26 and trailing edge 28. Cross sections have corresponding chords and bending lines. To improve performance characteristics, centers of gravity 34 of sections are leveled along axis of laying having double bend. EFFECT: improved characteristics. 14 cl, 5 dwg
| Title | Year | Author | Number |
|---|---|---|---|
| CURVED BLADE OF COMPRESSOR | 2000 |
|
RU2220329C2 |
| HIGH-EFFICIENCY LOW-NOISE LOW-PRESSURE COMPRESSOR OF HIGH BYPASS RATIO GAS TURBINE ENGINE | 2007 |
|
RU2350787C2 |
| TURBOJET LOW-PRESSURE COMPRESSOR ROTOR IMPELLER BLADE | 2014 |
|
RU2565135C1 |
| TURBOJET LOW-PRESSURE COMPRESSOR ROTOR IMPELLER BLADE | 2014 |
|
RU2565123C1 |
| TURBOJET LOW-PRESSURE COMPRESSOR ROTOR IMPELLER BLADE | 2014 |
|
RU2565138C1 |
| TURBOJET LOW-PRESSURE COMPRESSOR ROTOR IMPELLER BLADE | 2014 |
|
RU2565092C1 |
| BLADE WITH NARROW MIDDLE PART | 2000 |
|
RU2219377C2 |
| TURBOMACHINE ROTOR BLADE | 2013 |
|
RU2635734C2 |
| TURBOMACHINE ROTOR BLADE, DISC WITH BLADES, ROTOR AND TURBOMACHINE | 2016 |
|
RU2727823C2 |
| GAS TURBINE ENGINE STRAIGHTENER BLADE | 2014 |
|
RU2662761C2 |
